CN108318763A - A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator - Google Patents
A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator Download PDFInfo
- Publication number
- CN108318763A CN108318763A CN201810168113.0A CN201810168113A CN108318763A CN 108318763 A CN108318763 A CN 108318763A CN 201810168113 A CN201810168113 A CN 201810168113A CN 108318763 A CN108318763 A CN 108318763A
- Authority
- CN
- China
- Prior art keywords
- radiation
- simulator
- electric propulsion
- satellite
- frequency
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/001—Measuring interference from external sources to, or emission from, the device under test, e.g. EMC, EMI, EMP or ESD testing
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- General Physics & Mathematics (AREA)
- Plasma Technology (AREA)
Abstract
A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator individually carries out emc testing to configuring standby electric propulsion system, obtains the radiation-emitting parameter of the electric propulsion system under true ignition condition under vacuum；Secondly electric propulsion electromagnetic radiation simulator is built according to parameters obtained；Emc testing and assessment are carried out to satellite simultaneously, the Electro Magnetic Compatibility of satellite is judged according to the disturbed situation of electric propulsion system satellite, the verification to Electro Magnetic Compatibility is completed by above three step, reliability is high, and stability is good.
Description
Technical field
The present invention relates to a kind of Electro Magnetic Compatibility verification methods based on electric propulsion radiation-emitting simulator, and it is simultaneous to belong to electromagnetism
Hold experimental technique field.
Background technology
Electric propulsion system has the characteristics that high specific impulse, low thrust as a kind of advanced satellite booster technology, can be effective
Promote the bearing capacity and control accuracy of spacecraft, it has also become the standard configuration of each advanced spacecraft of astropower.
Electric propulsion system igniting requires to carry out under conditions of vacuum environment and configuration plasma safeguard, and satellite
Electro Magnetic Compatibility verification should carry out in the Electro Magnetic Compatibility laboratory of profession.The Electro Magnetic Compatibility verification test equipment of profession cannot
There is provided vacuum environment, therefore can not under the true ignition condition of electric propulsion the satellite of direct measuring configuration electric propulsion system electricity
Magnetic compatibility.Electro Magnetic Compatibility to complete the satellite of configuration electric propulsion system is verified, and design is needed to utilize ground-based simulation equipment
The scheme measured indirectly.
The following electric propulsion technology will be widely used in the fields such as manned space station, high rail satellite, survey of deep space, assessment reconciliation
Certainly the electromagnetic compatibility problem of electric propulsion work and satellite is the basis of the technology popularization and application.Currently for new electric propulsion technology
The compatibility for lacking reasonable directly tests evaluation measures, and current technology does not have system testing electric propulsion on whole star
Compatible sexuality is badly in need of designing a set of evaluation system for being compatible with whole star according to the true electromagnetic radiation feature of electric propulsion.
Invention content
Present invention solves the technical problem that being：For the electromagnetic compatibility disposition in the prior art to electric propulsion operational satellites
The problem of condition lacks feasible test appraisal procedure and allows the vacuum firing environment of test, it is proposed that one kind being based on electric propulsion spoke
Penetrate the Electro Magnetic Compatibility verification method of launching simulator.
The present invention solves above-mentioned technical problem and is achieved by following technical solution：
A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator, steps are as follows：
(1) the radiation-emitting parameter under electric thruster fired state is obtained by measurement；
(2) the radiation-emitting parameter obtained by step (1), which builds to have, has spoke in the full working frequency range of electric propulsion satellite
Penetrate the launching simulator of emissivities；
(3) emc testing and assessment are carried out to the launching simulator of step (2) structure, according to electric propulsion satellite
Disturbed situation judges the Electro Magnetic Compatibility of whole star.
In the step (1), the radiation-emitting parameter obtained under electric thruster fired state is as follows：
Electric thruster is placed in wave transparent cabin and vacuumized in cabin by (1a)；
(1b) carries out the electric thruster igniting under vacuum environment；
(1c) installs reception antenna respectively at the electric thruster back side outside wave transparent nacelle and side；
(1d) measures reception antenna using measuring instrument and collects electric propulsion device electromagnetic radiation data characteristic, generates full range
The amplitude information of each measurement frequency point in domain and corresponding frequency point, while obtaining the radiation-emitting parameter of electric thruster.
In the step (2), builds launching simulator and be as follows：
The electric thruster radiation-emitting parameter of (2a) obtained by step (1) provides radiating bands and radiation field for signal source
By force；
(2b) is made up of according to step (2a) parameters obtained signal source, adjustable attenuator, power amplifier and antenna
Electric propulsion radiation-emitting simulator, by the electromagnetic signal of antenna by externally emitting after enhanced processing and realizing simulation thruster
The wideband of working characteristics emits.
In the step (3), emc testing is carried out to satellite and is as follows with assessment：
Launching simulator is placed in wave transparent cabin according to radiation-emitting parameter obtained by step (2) and is positioned over EMC realities by (3a)
It tests under room environmental, reception antenna is installed respectively at the launching simulator back side outside wave transparent nacelle and side, to simulating in-orbit normal work
The launching simulator horizontal direction for making state applies Radiative EMI, and the Radiative EMI amount is EMC laboratory environments
Twice of magnitude of lower electromagnetic radiation experimental test range maximum value；
(3b) is in the field strength number within the scope of fixed frequency range away from erection field intensity probe at launching simulator 0.3m~1m and confirmation
Value is fixed value；
The radio field intensity that (3c) is received by reception antenna outside wave transparent nacelle with frequency situation of change confirm satellite by
Disturb magnitude；
(3d) judges whether the electromagnetic wave signal frequency range that reception antenna receives and electromagnetic radiation are higher than predetermined threshold value, if high
In predetermined threshold value, then the satellite Electro Magnetic Compatibility is unqualified；Otherwise, it is determined that the satellite Electro Magnetic Compatibility is qualified.
In the step (3d), satellite Electro Magnetic Compatibility predetermined threshold value is：
(S1) when launching simulator tranmitting frequency be more than or equal to 30MHz and less than 1GHz when, satellite allow radiate the upper limit be
120dB μ V/m, electric propulsion electromagnetic radiation limit value are 70dB μ V/m；
(S2) when launching simulator tranmitting frequency is more than or equal to 1.60GHz and less than 1.67GHz, satellite allows in radiation
25dB μ V/m are limited to, electric propulsion electromagnetic radiation limit value is 25dB μ V/m, and frequency range is L frequency ranges；
(S3) when launching simulator tranmitting frequency is more than or equal to 1.98GHz and less than 2.01GHz, satellite allows in radiation
25dB μ V/m are limited to, electric propulsion electromagnetic radiation limit value is 20dB μ V/m, and frequency range is L frequency ranges；
(S4) when launching simulator tranmitting frequency is more than or equal to 5.85GHz and less than 6.725GHz, satellite allows to radiate
The upper limit is 35dB μ V/m, and electric propulsion electromagnetic radiation limit value is 35dB μ V/m, and frequency range is C frequency ranges；
(S5) when launching simulator tranmitting frequency is more than or equal to 12.75GHz and is less than 13GHz, is more than or equal to 13.75GHz
And less than 14.5GHz, when being more than or equal to 17.3GHz and being less than 17.8GHz, satellite allows to radiate the upper limit to be 35dB μ V/m, and electricity pushes away
It is 35dB μ V/m into electromagnetic radiation limit value, frequency range is Ku frequency ranges；
(S6) when launching simulator tranmitting frequency is more than or equal to 18GHz and less than 22.5GHz, satellite allows to radiate the upper limit
For 120dB μ V/m, electric propulsion electromagnetic radiation limit value is 55dB μ V/m, and frequency range is Ka frequency ranges；
(S7) when launching simulator tranmitting frequency is more than or equal to 22.5GHz and less than 26.5GHz, satellite allows in radiation
40dB μ V/m are limited to, electric propulsion electromagnetic radiation limit value is 38dB μ V/m, and frequency range is Ka frequency ranges；
(S8) when launching simulator tranmitting frequency is more than or equal to 26.5GHz and less than 31GHz, satellite allows to radiate the upper limit
For 40dB μ V/m, electric propulsion electromagnetic radiation limit value is 38dB μ V/m, and frequency range is Ka frequency ranges.
When the launching simulator tranmitting frequency is more than or equal to 30MHz and is less than 1GHz, launching simulator selects preamplifier
With period logarithm antenna；When the launching simulator tranmitting frequency is more than or equal to 1GHz and is less than 18GHz, launching simulator is selected
Preamplifier and double-ridged horn antenna are realized；When the launching simulator tranmitting frequency is more than or equal to 18GHz and is less than 26.5GHz,
Launching simulator is selected to put in advance and be realized with electromagnetic horn；The launching simulator tranmitting frequency is more than or equal to 26.5GHz and is less than
When 40GHz, launching simulator is selected to put in advance and be realized with electromagnetic horn.
The electric thruster supply voltage is 1000V ± 10V, and screen-grid current is 0.8A ± 0.05A.
The electric thruster gas supply flow is 1.362 ± 5%mg/s.
The electric thruster tranmitting frequency fluctuation range is 30MHz~31GHz.
Preferably, the electric thruster electromagnetic radiation limits are 10~70dB μ V/m.
The advantages of the present invention over the prior art are that：
(1) the present invention provides a kind of Electro Magnetic Compatibility verification methods based on electric propulsion radiation-emitting simulator, solve
The demand that electric propulsion system can only light a fire in vacuum environment cannot with existing satellite electromagnetic compatibility test detection method
The contradiction between vacuum environment is provided, the satellite to configure electric propulsion system carries out the test of whole star Electro Magnetic Compatibility and assessment carries
Approach is supplied；
(2) the present invention provides the electromagnetic compatibility judgment criterions of satellite, believe for the transmitting electromagnetic wave in fixed range
The radiation-emitting amount of number frequency range and launching simulator, providing radiation-emitting amount limit grade value and satellite allows radiation value thresholding, protects
It has demonstrate,proved satellite and may determine that the amount of radiation that will not be worked by electric propulsion in the satellite other equipment course of work in restriction threshold value
Grade influences.
Description of the drawings
Fig. 1 is the compatibility verification method flow diagram that invention provides；
Fig. 2 is the wave transparent cabin structure schematic layout pattern that invention provides；
Fig. 3 is the electric propulsion system configuration schematic layout pattern that invention provides；
Fig. 4 is the launching simulator reality output frequency range and intensity that invention provides；
Specific implementation mode
A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator, based on the test in the darkrooms EMC
System is tested, as shown in Figure 1, wherein measurand is to be configured with the satellite of electric propulsion system, while needing to put on satellite
It sets in the darkrooms EMC, including power supply, air supply system, while the experiment of compatibility test are room temperature, condition of normal pressure, ion thrust
Two equipment of device load simulator are placed in by star, are connect with host computer by communication cable.Ion thruster load simulator
Power source loads characteristic for simulating ion thruster, the band for matching ADU carry characteristic, pass through the realization pair of load simulator host computer
The communication and control of ion thruster fictitious load device；Meanwhile arranging that antenna sets simulator generates at satellite+X identity distances are from 1 meter
Radiative EMI, i.e. electromagnetic interference receiver provide frequency and field strength according to electric thruster radiation-emitting parameter, to preamplifier
Input, preamplifier externally emits electromagnetic wave using antenna according to frequency and field strength, simulates and radiated under electric thruster fired state
The operating mode of transmitting, and field intensity probe is being set up at electric propulsion 0.1m~3m, ensure the interference strength that field intensity probe monitors
Meet the requirement of electric propulsion electromagnetic radiation magnitude, utilizes receiver to record test result at this time, signal data is received by receiver
With launching simulator transmitting electromagnetic wave signal data monitoring satellite it is whether disturbed, while judge satellite Electro Magnetic Compatibility whether
It is qualified.
Specific method flow is as shown in Fig. 2, steps are as follows：
(1) the radiation-emitting parameter under electric thruster fired state is obtained by measurement, wherein operating process is as follows：
Electric thruster is placed in wave transparent cabin and vacuumized in cabin by (1a), and vacuum degree is better than 1 × 10-3Pa；；
(1b) carries out the electric thruster igniting under vacuum environment, and electric thruster igniting requires to keep stable power supply and gas supply
Environment, power supply screen-grid voltage are stablized in 1000V ± 10V, and screen-grid current is stablized in 0.8A ± 0.05A, and total gas supply flow is stablized
1.362 ± 5%mg/s；
(1c) installs reception antenna respectively at the electric thruster back side outside wave transparent nacelle and side；
(1d) measures the radiation-emitting parameter for the electric thruster that reception antenna receives respectively using measuring instrument.
(2) the transmitting radiation parameter obtained by step (1), which is built to have, has radiation-emitting in the full working frequency range of satellite
The launching simulator of ability, wherein operating process are as follows：
The electric thruster radiation-emitting parameter of (2a) obtained by step (1) provides radiating bands and radiation field for signal source
By force；
(2b) is made up of according to step (2a) parameters obtained signal source, adjustable attenuator, power amplifier and antenna
Electric propulsion radiation-emitting simulator, by the electromagnetic signal of antenna by externally emitting after enhanced processing and realizing simulation thruster
The wideband of working characteristics emits；
(3) emc testing and assessment are carried out to satellite, is defended according to the judgement of the disturbed situation of electric propulsion system satellite
The Electro Magnetic Compatibility of star, wherein operating process are as follows：
Launching simulator is placed in wave transparent cabin according to radiation-emitting parameter obtained by step (2) and is positioned over EMC realities by (3a)
It tests under room environmental, reception antenna is installed respectively at the launching simulator back side outside wave transparent nacelle and side, to simulating in-orbit normal work
The launching simulator horizontal direction for making state applies Radiative EMI, and the Radiative EMI amount is EMC laboratory environments
Twice of magnitude of lower electromagnetic radiation experimental test range maximum value；
(3b) is in the field strength number within the scope of fixed frequency range away from erection field intensity probe at launching simulator 0.3m~1m and confirmation
Value is fixed value；
The radio field intensity that (3c) is received by reception antenna outside wave transparent nacelle with frequency situation of change confirm satellite by
Disturb magnitude；
(3d) judges whether the electromagnetic wave signal frequency range that reception antenna receives and electromagnetic radiation are higher than predetermined threshold value, if high
In predetermined threshold value, then the satellite Electro Magnetic Compatibility is unqualified；Otherwise, it is determined that the satellite Electro Magnetic Compatibility is qualified.
In the step (3d), the electromagnetic wave signal frequency range approximate range of launching simulator transmitting is 30MHz~31GHz,
Radiation-emitting order magnitude range 10~70dB μ V/m, in same band limits, the electromagnetism for the electromagnetic wave signal that receiver receives
Radiation value and satellite integrally allow the radiation upper limit to be respectively less than given threshold, then are considered as Electro Magnetic Compatibility qualification, are otherwise considered as and do not conform to
Lattice, specific criterion such as following table：
(S1) when launching simulator tranmitting frequency be more than or equal to 30MHz and less than 1GHz when, satellite allow radiate the upper limit be
120dB μ V/m, electric propulsion electromagnetic radiation limit value are 70dB μ V/m；
(S2) when launching simulator tranmitting frequency is more than or equal to 1.60GHz and less than 1.67GHz, satellite allows in radiation
25dB μ V/m are limited to, electric propulsion electromagnetic radiation limit value is 25dB μ V/m, and frequency range is L frequency ranges；
(S3) when launching simulator tranmitting frequency is more than or equal to 1.98GHz and less than 2.01GHz, satellite allows in radiation
25dB μ V/m are limited to, electric propulsion electromagnetic radiation limit value is 20dB μ V/m, and frequency range is L frequency ranges；
(S4) when launching simulator tranmitting frequency is more than or equal to 5.85GHz and less than 6.725GHz, satellite allows to radiate
The upper limit is 35dB μ V/m, and electric propulsion electromagnetic radiation limit value is 35dB μ V/m, and frequency range is C frequency ranges；
(S5) when launching simulator tranmitting frequency is more than or equal to 12.75GHz and is less than 13GHz, is more than or equal to 13.75GHz
And less than 14.5GHz, when being more than or equal to 17.3GHz and being less than 17.8GHz, satellite allows to radiate the upper limit to be 35dB μ V/m, and electricity pushes away
It is 35dB μ V/m into electromagnetic radiation limit value, frequency range is Ku frequency ranges；
(S6) when launching simulator tranmitting frequency is more than or equal to 18GHz and less than 22.5GHz, satellite allows to radiate the upper limit
For 120dB μ V/m, electric propulsion electromagnetic radiation limit value is 55dB μ V/m, and frequency range is Ka frequency ranges；
(S7) when launching simulator tranmitting frequency is more than or equal to 22.5GHz and less than 26.5GHz, satellite allows in radiation
40dB μ V/m are limited to, electric propulsion electromagnetic radiation limit value is 38dB μ V/m, and frequency range is Ka frequency ranges；
(S8) when launching simulator tranmitting frequency is more than or equal to 26.5GHz and less than 31GHz, satellite allows to radiate the upper limit
For 40dB μ V/m, electric propulsion electromagnetic radiation limit value is 38dB μ V/m, and frequency range is Ka frequency ranges.
In different frequency range, launching simulator selects different types of reception antenna, as shown in figure 3, specific choice situation
It is as follows：
(a) when the launching simulator tranmitting frequency is more than or equal to 30MHz and is less than 1GHz, launching simulator selection is put in advance
Device and period logarithm antenna；
(b) when the launching simulator tranmitting frequency is more than or equal to 1GHz and is less than 18GHz, launching simulator selection is put in advance
Device and double-ridged horn antenna are realized；
(c) when the launching simulator tranmitting frequency is more than or equal to 18GHz and is less than 26.5GHz, launching simulator is selected
Pre- put is realized with electromagnetic horn；
(d) when the launching simulator tranmitting frequency is more than or equal to 26.5GHz and is less than 40GHz, launching simulator is selected
Pre- put is realized with electromagnetic horn.
(4) to the susceptibility test of satellite certain sensitive equipment, according to the disturbed feelings of electric propulsion system satellite specific load
Condition judges that the Electro Magnetic Compatibility of satellite, wherein operating process are as follows：
(4a) carries out sensitive equipment field strength monitoring, i.e., sets up field intensity probe at 0.3~1m near Satellite is quick and ground is quick,
Under the interference field strength of record simulation electric propulsion working environment, the quick field strength at the quick position in ground of star, assessment judges configuration electric propulsion
The compatibility of the satellite sensitive equipment of system.
(4b) influences monitoring as shown in figure 4, carrying out the frequency acceptance band of receiver, that is, tests under electric propulsion simulation working environment
When the disturbed situation of satellite band, setting interference field strength threshold requirement is as follows：Usual satellite RF frequency acceptance band connects for observing and controlling
When receiving frequency band, setting interference field strength threshold value is not lower than 2V/m in the test frequency range；The satellite RF being related to is communicated to receive
When frequency band is communication band, setting interference field strength threshold value is not lower than 4V/m in the test frequency range；Field intensity probe is located at quick
At position, whole star power-up procedures maximum field strength threshold value is not lower than 4V/m.
The content that description in the present invention is not described in detail belongs to the known technology of those skilled in the art.
Claims (10)
1. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator, it is characterised in that steps are as follows：
(1) the radiation-emitting parameter under electric thruster fired state is obtained by measurement；
(2) the radiation-emitting parameter obtained by step (1), which builds to have in the full working frequency range of electric propulsion satellite, has radiation hair
Penetrate the launching simulator of ability；
(3) emc testing and assessment are carried out to the launching simulator of step (2) structure, according to the disturbed of electric propulsion satellite
Situation judges the Electro Magnetic Compatibility of whole star.
2. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 1,
It is characterized in that：In the step (1), the radiation-emitting parameter obtained under electric thruster fired state is as follows：
Electric thruster is placed in wave transparent cabin and vacuumized in cabin by (1a)；
(1b) carries out the electric thruster igniting under vacuum environment；
(1c) installs reception antenna respectively at the electric thruster back side outside wave transparent nacelle and side；
(1d) measures reception antenna using measuring instrument and collects electric propulsion device electromagnetic radiation data characteristic, generates full frequency-domain
The amplitude information of each measurement frequency point and corresponding frequency point, while obtaining the radiation-emitting parameter of electric thruster.
3. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 2,
It is characterized in that：In the step (2), builds launching simulator and be as follows：
The electric thruster radiation-emitting parameter of (2a) obtained by step (1) provides radiating bands and radiation field intensity for signal source；
(2b) passes through the electricity of signal source, adjustable attenuator, power amplifier and antenna composition according to step (2a) parameters obtained
Radiation-emitting simulator is promoted, by the electromagnetic signal of antenna by externally emitting and realizing simulation thruster work after enhanced processing
The wideband of characteristic emits.
4. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 3,
It is characterized in that：In the step (3), emc testing is carried out to satellite and is as follows with assessment：
Launching simulator is placed in wave transparent cabin according to radiation-emitting parameter obtained by step (2) and is positioned over the laboratories EMC by (3a)
Under environment, reception antenna is installed respectively at the launching simulator back side outside wave transparent nacelle and side, to simulating in-orbit normal work shape
The launching simulator horizontal direction of state applies Radiative EMI, and the Radiative EMI amount is electricity under EMC laboratory environments
Twice of magnitude of magnetic radiation experimental test range maximum value；
(3b) is in the field strength numerical value within the scope of fixed frequency range away from erection field intensity probe at launching simulator 0.3m~1m and confirmation
Fixed value；
(3c) confirms the disturbed amount of satellite by the radio field intensity that reception antenna outside wave transparent nacelle receives with frequency situation of change
Grade；
(3d) judges whether the electromagnetic wave signal frequency range that reception antenna receives and electromagnetic radiation are higher than predetermined threshold value, if higher than pre-
If then the satellite Electro Magnetic Compatibility is unqualified for threshold value；Otherwise, it is determined that the satellite Electro Magnetic Compatibility is qualified.
5. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 4,
It is characterized in that：In the step (3d), satellite Electro Magnetic Compatibility predetermined threshold value is：
(S1) when launching simulator tranmitting frequency is more than or equal to 30MHz and less than 1GHz, satellite allows to radiate the upper limit to be 120dB
μ V/m, electric propulsion electromagnetic radiation limit value are 70dB μ V/m；
(S2) when launching simulator tranmitting frequency be more than or equal to 1.60GHz and less than 1.67GHz when, satellite allow radiate the upper limit be
25dB μ V/m, electric propulsion electromagnetic radiation limit value are 25dB μ V/m, and frequency range is L frequency ranges；
(S3) when launching simulator tranmitting frequency be more than or equal to 1.98GHz and less than 2.01GHz when, satellite allow radiate the upper limit be
25dB μ V/m, electric propulsion electromagnetic radiation limit value are 20dB μ V/m, and frequency range is L frequency ranges；
(S4) when launching simulator tranmitting frequency is more than or equal to 5.85GHz and less than 6.725GHz, satellite allows to radiate the upper limit
For 35dB μ V/m, electric propulsion electromagnetic radiation limit value is 35dB μ V/m, and frequency range is C frequency ranges；
(S5) when launching simulator tranmitting frequency be more than or equal to 12.75GHz and less than 13GHz, be more than or equal to 13.75GHz and small
In 14.5GHz, when being more than or equal to 17.3GHz and being less than 17.8GHz, satellite allows to radiate the upper limit to be 35dB μ V/m, electric propulsion electricity
Magnetic radiation limit value is 35dB μ V/m, and frequency range is Ku frequency ranges；
(S6) when launching simulator tranmitting frequency be more than or equal to 18GHz and less than 22.5GHz when, satellite allow radiate the upper limit be
120dB μ V/m, electric propulsion electromagnetic radiation limit value are 55dB μ V/m, and frequency range is Ka frequency ranges；
(S7) when launching simulator tranmitting frequency be more than or equal to 22.5GHz and less than 26.5GHz when, satellite allow radiate the upper limit be
40dB μ V/m, electric propulsion electromagnetic radiation limit value are 38dB μ V/m, and frequency range is Ka frequency ranges；
(S8) when launching simulator tranmitting frequency be more than or equal to 26.5GHz and less than 31GHz when, satellite allow radiate the upper limit be
40dB μ V/m, electric propulsion electromagnetic radiation limit value are 38dB μ V/m, and frequency range is Ka frequency ranges.
6. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 5,
It is characterized in that：When the launching simulator tranmitting frequency is more than or equal to 30MHz and is less than 1GHz, launching simulator selects preamplifier
With period logarithm antenna；When the launching simulator tranmitting frequency is more than or equal to 1GHz and is less than 18GHz, launching simulator is selected
Preamplifier and double-ridged horn antenna are realized；When the launching simulator tranmitting frequency is more than or equal to 18GHz and is less than 26.5GHz,
Launching simulator is selected to put in advance and be realized with electromagnetic horn；The launching simulator tranmitting frequency is more than or equal to 26.5GHz and is less than
When 40GHz, launching simulator is selected to put in advance and be realized with electromagnetic horn.
7. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 1,
It is characterized in that：The electric thruster supply voltage is 1000V ± 10V, and screen-grid current is 0.8A ± 0.05A.
8. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 7,
It is characterized in that：The electric thruster gas supply flow is 1.362 ± 5%mg/s.
9. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 8,
It is characterized in that：The electric thruster tranmitting frequency fluctuation range is 30MHz~31GHz.
10. a kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator according to claim 9,
It is characterized in that：The electric thruster electromagnetic radiation limits are 10~70dB μ V/m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810168113.0A CN108318763A (en) | 2018-02-28 | 2018-02-28 | A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810168113.0A CN108318763A (en) | 2018-02-28 | 2018-02-28 | A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108318763A true CN108318763A (en) | 2018-07-24 |
Family
ID=62901817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810168113.0A Pending CN108318763A (en) | 2018-02-28 | 2018-02-28 | A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108318763A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113408106A (en) * | 2021-05-27 | 2021-09-17 | 北京国电高科科技有限公司 | Ender-sky constellation communication load EMC analysis model and EMC characteristic improvement method |
| CN114325173A (en) * | 2021-12-07 | 2022-04-12 | 中国空间技术研究院 | Universal testing device and method for spacecraft system-level electromagnetic radiation emission |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102435872A (en) * | 2011-09-06 | 2012-05-02 | 航天东方红卫星有限公司 | Method for verifying radiation electromagnetic compatibility of electric propulsion system and satellite |
| CN105659849B (en) * | 2012-05-28 | 2014-08-13 | 北京空间飞行器总体设计部 | A kind of cut-out method of satellite system level electromagnetic compatible radiosensitivity control criterion |
-
2018
- 2018-02-28 CN CN201810168113.0A patent/CN108318763A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102435872A (en) * | 2011-09-06 | 2012-05-02 | 航天东方红卫星有限公司 | Method for verifying radiation electromagnetic compatibility of electric propulsion system and satellite |
| CN105659849B (en) * | 2012-05-28 | 2014-08-13 | 北京空间飞行器总体设计部 | A kind of cut-out method of satellite system level electromagnetic compatible radiosensitivity control criterion |
| CN105659848B (en) * | 2012-05-28 | 2014-10-22 | 北京空间飞行器总体设计部 | A kind of cut-out method for system-level radiation-emitting control criterion |
Non-Patent Citations (1)
| Title |
|---|
| 中国人民解放军总装备部: "《GJB151B-2013》", 10 July 2013 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113408106A (en) * | 2021-05-27 | 2021-09-17 | 北京国电高科科技有限公司 | Ender-sky constellation communication load EMC analysis model and EMC characteristic improvement method |
| CN114325173A (en) * | 2021-12-07 | 2022-04-12 | 中国空间技术研究院 | Universal testing device and method for spacecraft system-level electromagnetic radiation emission |
| CN114325173B (en) * | 2021-12-07 | 2024-04-05 | 中国空间技术研究院 | Universal testing device and method for spacecraft system-level electromagnetic radiation emission |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Arai | Measurement of mobile antenna systems | |
| CN108205089A (en) | A kind of whole star Electro Magnetic Compatibility verification method and system based on electric propulsion radiation-emitting simulator | |
| CN103048561B (en) | EMC (Electro Magnetic Compatibility) test method of deep space aircraft coupling | |
| CN104392023B (en) | Aircraft nacelle electromagnetic model method of calibration under the conditions of a kind of high high radiation field | |
| KR20100053482A (en) | Multichannel absorberless near field measurement system | |
| CN109655671B (en) | High-intensity radiation field effect test system and test method for low-level sweep current | |
| CN103336192A (en) | A low-level scanning current testing system for an aircraft whole body | |
| CN108318763A (en) | A kind of Electro Magnetic Compatibility verification method based on electric propulsion radiation-emitting simulator | |
| US10267837B2 (en) | Electromagnetic radiation detection apparatus and method of detecting low levels of millimeter wave electromagnetic radiation | |
| CN109085431A (en) | Test macro and test method | |
| CN103063939B (en) | Ground cascade system external radio frequency electromagnetic environment test method | |
| Wang et al. | Study on capability verification test of electromagnetic pulse protection for aircraft | |
| Gandolfo et al. | Improving the accuracy of radiated emission measurements for frequency below 30 MHz by using a fiber optic isolated rod antenna | |
| Larsen et al. | Design and Calibration of the NBS Isotropic Electric-Field Monitor [EFM-5], 0.2 to 1000 MHz | |
| Kuriger et al. | Investigation of spurious emissions from cellular phones and the possible effect on aircraft navigation equipment | |
| JP2005241421A (en) | Interference excluding capability testing apparatus | |
| Heidemann et al. | Using TEM waveguides according to the new IEC 61000-4-20 | |
| Carobbi et al. | Low-Uncertainty Characterization of a Predictable Active and Broadband Antenna | |
| Pous et al. | Characterization of Time Domain EM Field Double-loaded Curved Loop Probe | |
| Dybdal | Communication satellite antenna testing | |
| Moraitis et al. | Electric field uniformity in a GTEM cell for in-vitro exposure studies: simulations and measurements | |
| Trout | Launch Vehicle and Spacecraft Transmitter Electromagnetic Compatibility | |
| Moradmand et al. | Utilizing FM and TV Transmitters for Characterizing Shielded Enclosures | |
| You et al. | Spacecraft Antenna Test Technology | |
| Zhao et al. | Hints and ideas on customising the EMC engineering approach for CubeSat projects |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20180724 |